GPS attitude system integrated with an inertial system for space applications

Gelderloos, H.; Sheikh, Suneel I.; Schipper, Brian

doi:10.1109/dasc.1997.637253

Cited by 4 publications

(3 citation statements)

References 1 publication

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“…Finally, JSC is sponsoring the development and qualification of a NASA Space Integrated GPS/ INS called SIGI. 46,47 Honeywell is under contract to JSC to develop this standardized, highly-integrated, autonomous navigation system with a GPS position, velocity, and attitude capability integrated with an advanced inertial system. It has a Trimble TANS Vector GPS receiver coupled with a Honeywell H-764G Inertial Measurement Unit (IMU).…”

Section: Today's Technology and Ongoing Technology Efforts Relatementioning

confidence: 99%

“…A good choice for a GPS/INS system is the SIGI that is being developed for applications like the Space Shuttle, the ISS, and the CRV. 46,47 It generates position, linear velocity, inertial attitude, and angular velocity with absolute GPS. These are used to get the chase vehicle to within about 7 kilometers of the target vehicle.…”

Section: Proposed Automated Rendezvous and Capture Systems For Meementioning

confidence: 99%

See 1 more Smart Citation

Technology of Automated Rendezvous and Capture in Space

Polites

1999

Journal of Spacecraft and Rockets

111

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Section: Today's Technology and Ongoing Technology Efforts Relatementioning

confidence: 99%

Section: Proposed Automated Rendezvous and Capture Systems For Meementioning

confidence: 99%

Technology of Automated Rendezvous and Capture in Space

Polites

1999

Journal of Spacecraft and Rockets

111

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“…Evans et al [3] show a configuration of the integrated navigation system for an unmanned aerial vehicle (UAV) using an inertial measurement unit (IMU) and an ADGPS receiver as a subsystem of the autopilot system in the 'DragonFly' project. Wolf et al [4] describe an integrated GPS/INS system that consists of a low cost IMU and an ADGPS receiver, 'TANS Vector' from Trimble Navigation Ltd. Gelderloos et al [5] discussed a GPS attitude system integrated with inertial sensors for space applications. Gebre-Egziabher et al [6] have introduced an inexpensive attitude heading reference system (AHRS), in which low cost automotive grade inertial sensors are integrated with an ADGPS receiver with ultra-short baseline antenna scheme.…”

Section: Introductionmentioning

confidence: 99%

Attitude Determination GPS/INS Integration System Design Using Triple Difference Technique

Oh¹,

Hwang²,

Park³

et al. 2012

Journal of Electrical Engineering and Technology

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-GPS attitude outputs or carrier phase observables can be effectively utilized to compensate the attitude error of the strapdown inertial navigation system. However, when the integer ambiguity is not correctly resolved and/or a cycle slip occurs, an erroneous GPS output can be obtained. If the erroneous GPS output is applied to the attitude determination GPS/INS (ADGPS/INS) integrated navigation system, the performance of the system can be degraded. This paper proposes an ADGPS/INS integration system using the triple difference carrier phase observables. The proposed integration system contains a cycle slip detection algorithm, in which the inertial information is combined. Computer simulations and flight test were performed to verify effectiveness of the proposed navigation system. Results show that the proposed system gives an accurate and reliable navigation solution even when the integer ambiguity is not correctly resolved and the cycle slip occurs.

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